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本文叙述飞行器的再入热环境、烧蚀、传热和热应力等的综合分析计算原理及一些处理技巧。对碳基材料烧蚀表面的化学反应,利用选择性计算的结果简化了热化学烧蚀计算,采用等距和不等距的三层显式差分格式计算温度场;热应力是在线弹性假设下根据不完全的广义位能原理用有限元法计算的,可计算多种位移边界条件的影响。在编制的综合分析程序中,实现了一种自动划分网格技术,有利于选形计算。
This article describes the re-entry aircraft thermal environment, ablation, heat transfer and thermal stress, such as a comprehensive analysis and calculation principle and some processing techniques. The chemical reaction on the ablated surface of carbon-based materials is simplified by using the results of selective calculation. The three-layer explicit difference scheme is used to calculate the temperature field. The thermal stress is based on the on-line elastic assumption According to the principle of incomplete generalized potential energy calculated by the finite element method, the influence of various displacement boundary conditions can be calculated. In the preparation of a comprehensive analysis program, to achieve an automatic meshing technology is conducive to shape selection calculations.